An aircraft airfoil or wing or fuselage MODULE is fitted with a gas turbine engine driving a fan or propeller, in combination with a gaseous pressure accumulator, wherein said fan or propeller and said gaseous pressure accumulator both provide thrust, said fan thrust being provided from a rear of the MODULE via a drop-down thrust vectoring panel and said gaseous pressure accumulator thrust being provided from a fore of said MODULE, wherein the gaseous pressure accumulator is supplied with exhaust from said gas turbine engine and said exhaust is delivered downwardly at a variable angle, and said thrust vectoring panel is a panel with multiple minor panels which vector fan thrust at more than one angle. The gas turbine engine exhaust is delivered forwardly of said fan or propeller exhaust.
Vertical takeoff and landing aircraft and gas turbine engine with fan thrust and exhaust thrust delivered downwardly
2017-06-08
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
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